JP2007045398A - Aircraft system operating method - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To surely and efficiently control pressurization and control temperature in an aircraft cabin, and to supply fresh air independently of flight height. <P>SOLUTION: This is a method of operating an aircraft system having a first compressed air supply source structured of a first compressor filled with open air, ram air and/or pressurized air and to be driven at least one motor and/or at least one turbine and provided with an exhaust opening directly or indirectly communicated with the aircraft cabin. The aircraft system has at least one second compressed air supply source provided with an exhaust opening directly or indirectly connected to the aircraft cabin. In the first operation mode, only the first compressed air supply source is communicated with the aircraft cabin, and in the second operation mode, both the first and the second compressed air supply sources are communicated with the aircraft cabin. Operation mode is selected in response to the open air pressure, and when the open air pressure is high, the first operation mode is set, and when the open air pressure is low, the second operation mode is set. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

The present invention relates to a method of operating an aircraft system. In particular, for the purpose of fresh air supply, air conditioning and pressurization in aircraft cabins, filled with outside air, ram air and / or pressurized air and driven by at least one motor and / or at least one turbine, aircraft cabins The present invention relates to a method of operating an aircraft system including a first compressed air supply source configured by a first compressor having an exhaust port that communicates directly or indirectly. The aircraft system has at least one second compressed air source with an exhaust port that can communicate directly or indirectly with an aircraft cabin.

Various embodiments are known for aircraft air conditioning systems that include a compressor that operates using outside air. The aircraft air conditioning system described in Patent Document 1 has three heat exchangers installed in a ram air duct and connects them so that the cooling capacity changes, thereby cooling the compressed air in various ways. Do.
In the aircraft air conditioning system described in Patent Document 2, a mixed airflow formed by mixing a precooled extraction airflow and a compressed / precooled external airflow is supplied to an appropriate means and dehumidified. This mixed air flow dehumidifying means comprises an evaporator / condenser combined unit. The two airflows are mixed at the mixing point in this unit, but at this time the size of the droplets contained in the airflow increases. The aircraft air conditioning system described in Patent Document 3 operates without using bleed air, and a compressor filled with ram air or outside air is driven by a motor.
WO 2005/030585 A1 DE 102 34 968 A1 DE 103 50 541 A1

  The compressor filled with the outside air has a problem that ambient conditions such as the intake pressure of the compressor change remarkably depending on the flight altitude. For this reason, a wide operating range is required, but a single compressor cannot cope with this completely and effectively.

  It is an object of the present invention to reliably and efficiently carry out pressurization, temperature control and supply of fresh air in an aircraft cabin regardless of flight altitude by further developing the operation method of the aircraft air conditioning system.

  This object is achieved by a method with the features of claim 1. According to this configuration, only the first compressed air supply source communicates with the aircraft cabin in the first operation mode, and both the first and second compressed air supply sources communicate with the aircraft cabin in the second operation mode. The operation mode is selected according to the outside air pressure, and the first operation mode is set when the outside air pressure is high, and the second operation mode is set when the outside air pressure is relatively low. Thus, the method of the present invention functions in two or more modes of operation that are determined primarily by flight altitude and atmospheric pressure.

  In the first operation mode, only the first compressor is supplied with air. The first compressor may be, for example, a single stage compressor or a multistage compressor. This compressor reliably meets the requirements for pressurization, temperature control and fresh air supply during ground operation.

  In the second mode of operation, i.e. under low atmospheric pressure, such as during flight, the required fresh air mass can be provided from at least two sources. The two sources are the first compressor and another compressed air source that are filled with outside air and driven by a motor and / or turbine. The mixed air stream formed by mixing two masses from these compressed air sources is subjected to another process such as cooling and dehumidification before being supplied to the aircraft cabin, for example.

  The air is preferably cooled by at least one ram air heat exchanger and / or at least one turbine installed in the ram air duct of the aircraft before entering the aircraft cabin. In a first mode of operation, cooling is one or more expansions coupled to the at least one ram air heat exchanger, both integrated into the cooling process, and preferably to the first compressor and motor on one shaft. It is preferred to do so both with the turbine. One or more turbines may be installed on one shaft with the compressor. The cooling is preferably effected by a single device comprising one or more turbines thus incorporated into the cooling process.

  By providing multiple expansion stages or turbines with a compressor on one shaft, for example, one of the multiple turbines is used for cooling and the other turbine is used for energy recovery, for example, by expansion of cabin air The advantage is that it can be used for any purpose. Of course, all turbines of the ACM can be used for cooling. The way in which the individual expansion stages are used for different purposes is determined, for example, by specific parameters etc. and should not be the same under all conditions.

  In the second operation mode, the exhaust gas of the first compressed air supply source and at least a part of the exhaust gas of the second compressed air supply source are mixed, and the mixed airflow is cooled. This cooling can be performed with at least one ram air heat exchanger and at least one expansion turbine integrated into the cooling process, as in the first mode of operation.

The mixing point of both airflows is constituted by a chamber, for example. This chamber is, for example, a chamber for ozone or hydrocarbon conversion.
According to yet another concept of the invention, at least a portion of the exhaust of the first and / or second compressor or the exhaust of the second compressed air supply is supplied to the jet pump. The jet pump is disposed, for example, in a ram air duct of an aircraft and has a function of cooling a motor driving a ram air heat exchanger and / or a compressor.

  The second compressed air supply source may be constituted by one or more single-stage or multi-stage electric second compressors filled with outside air, ram air and / or pressurized air. Further, the second compressed air supply source may be constituted by engine bleed.

  The present invention is not limited to the first and second compressed air supply sources. It is also possible to connect as many additional compressed air sources as necessary.

  According to a preferred concept of the invention, a first compressed air supply and at least another further compressed air supply are connected in parallel. These compressed air supply sources may be, for example, compressors filled with outside air and connected in parallel.

  The advantages of the present invention are not only efficient operation of aircraft systems, particularly for fresh air supply, air conditioning and pressurization in aircraft cabins. In addition to this, there is a substantial advantage of a dual configuration with at least two compressed air sources per system. For example, even if a motor failure occurs in one compressor, the other compressed air supply source ensures sufficient supply to the aircraft cabin both during ground operation and in flight. A dual configuration is also formed in two aircraft systems or two aircraft air conditioning systems that are in communication with each other by a line (cross bleed duct structure), as described in detail below.

  The above description regarding the first and second operating modes or other operating modes applies to the normal case. When a malfunction such as a failure of the first compressor occurs, another connection different from this can be set. For example, when the first compressor fails, the second compressed air supply source supplies the aircraft cabin even if the first operating mode should actually be selected under the ambient conditions at that time. ing.

  According to still another concept of the present invention, a water extraction circuit is provided downstream of the compressed air supply source and upstream of the passenger cabin, and a turbine is provided downstream of the water extraction circuit. A third operating mode has been set in which both the compressed air supply communicates with the aircraft cabin and the compressed air is directed near the water extraction circuit and the turbine by partial or complete bypass. The supply of fresh air occurs at the beginning of this mode, similar to the first or second mode of operation. However, due to ambient conditions when the flight altitude is high, the water extraction circuit and the turbine stage are at least partially bypassed by opening the bypass valve. Thus, in this case, cooling is effected substantially via one or more ram air heat exchangers.

  According to yet another concept of the present invention, air enters at least one ram air heat exchanger installed in the ram air duct of the aircraft and one shaft with the first compressor before entering the aircraft cabin. Cooled by one or more expansion turbines installed above and filled in whole or in part. Cooling is preferably done by a single ACM with one or more ram air heat exchangers and one or more turbines integrated into the air cooling process. The one or more turbines are preferably coupled to the compressor and motor on one shaft.

  According to the invention, the second or another compressed air source is preferably switched from a constant altitude during the flight. They can therefore be used at least partially for cooling by the ram air heat exchanger on the ground. That is, it can be used in the first operation mode.

  In this process, some or all of the air extracted from the compressor may be supplied via a regulating valve or check valve to a jet pump incorporated in the fan chamber of the ram air duct. This jet pump ensures that the cooling air flow flows to the ram air heat exchanger. The jet pump may be configured in combination with a specific airflow cross-sectional shape and / or a specific sound absorption layer or the like as a sound absorption measure. The second compressed air supply source may be connected to the jet pump in an operation mode different from the first operation mode. In general, the first compressor can communicate with the jet pump regardless of the mode of operation.

  Alternatively, outside air intake may be performed via one or more ram air heat exchangers using impellers built into ram air ducts or fan chambers (plenums). The impeller is coupled with an electric compressor on one shaft. In this case, the air sent by the operating compressor may be blown out, may be utilized in the ram air duct to assist the fan via a jet pump, or another You may supply to a demand part.

  It is also possible to provide one or more fans independently of one or more compressors. One or more fans are used to cool one or more compressor motors and / or one or more ram air heat exchangers and are not coupled to the compressor or installed on one shaft with the compressor It is provided not to be done.

  The fan chamber may be configured to branch the air flow. In this step, the ram air duct has one or more bulkheads that extend at least partially in the flow direction to divide the ram air duct into at least two sections, the first section having a second compressed air. An impeller coupled to a jet pump or a second compressor in communication with the supply is disposed so that air passing through the ram air duct bypasses the first section by a second section. The cooling air of the ram air heat exchanger is preferably transferred to the first section under ground conditions. The jet pump and the impeller are arranged in this section, and may be arranged at one branch part or may be separately arranged at a plurality of adjacent branch parts. The cooling air of the ram air heat exchanger is preferably transferred to the second section under flight conditions. Bypassing the jet pump or impeller increases the delivery volume. If the fan is coupled to the compressor, this bypass, or another branch, assists in a safe ventilation operation in which recirculation flow occurs.

  Another section may be provided in the ram air duct provided with a jet pump and / or a fan for cooling the motor driving the compressor.

  According to yet another concept of the invention, a jet pump or fan is provided to cool one or more motors that drive one or more compressors.

  The switching time of the parallel compressors or compressed air sources can be determined by various criteria.

  When the compression limit of the first compressor is reached or when the maximum motor power of the first compressor is reached, switching from the first operation mode to the second mode can be performed. When the motors of all the compressors are the same size, switching to another compressor is performed at an early stage.

  In each unit, when the second compressor or the second or another source of compressed air is switched on, the mass of the first compressor is halved or reduced. This is because the stream sent from the second compressor or another source of compressed air does not meet the required amount of fresh air. As a result, at least for the first compressor, the new operating point is located in the unstable range on the left side of the pump limit (surge line). Various measures can be taken to enable safe or stable operation.

  In the second operation mode and the third operation mode, the amount of fresh air to the cabin can be increased. The amount of fresh air can generally be increased also in other operating modes, for example the first operating mode.

  The mass can also be increased by recirculation through the compressor stage. A valve (anti-surge valve (ASV)) can be provided in the recirculation line. This increase in the flow rate functions not only for increasing the amount of fresh air but for the safety of the components. Such recirculation may be independent of the mode of operation. That is, the selection can be made in the first, second, and third operation modes.

  Further, in the first or second mode of operation, the exhaust of the first compressor and / or the exhaust of the plurality of compressors may be routed to a second compressed air source and / or separate via a jet pump in the ram air duct of the aircraft. May be supplied to other compressed air sources, or may be supplied to yet another demand section of the aircraft. This method of operation is possible in the first or second operating mode, but is also possible in other operating modes.

  As a result, the compressor can be operated within a stable range in any desired mode.

  The further demand section is, for example, a system such as OBOGS, OBIGGS, WAI (anti-icing wing), or another heater / cooler. The exhaust can be used to start an engine or an auxiliary engine (APU).

  In order to limit the required motor power, the unit delivery may be increased depending on the required cooling capacity and the amount of air dehumidification by the water extraction circuit. Various means are available for this purpose.

  The required motor power may ideally be adjusted by adjusting the cross-sectional area using an adjustable turbine guide device. In designing the turbine nozzle, it is important to consider the time of ground operation with the maximum cooling capacity and high air humidity. It is necessary to increase the nozzle area as the flight altitude increases. This turbine guide device can be controlled, for example, electrically, electropneumatically or purely by pneumatic action.

  The delivery amount can be further increased. When the flight altitude is high and the outside air humidity is low, the water extraction circuit and the turbine are bypassed by opening the bypass line. This is because when the flight altitude is high, it is not necessary to dehumidify any more. The valve BPV is arranged in this bypass line. When the BPV is fully open, the delivery capacity of the bypass line is large and the turbine stage is almost completely bypassed, so the required cooling capacity should be achieved by the ram air heat exchanger. If higher turbine cooling capacity is required, additional turbine cooling capacity or other cooling capacity can be achieved by adjusting only the BPV. Therefore, the pressure ratio of the compressor increases and a larger motor power is required.

  A control unit common to the valve TCV provided in the line for connecting the exhaust port of the compressed air supply source or the gas mixture line to the exhaust port of the turbine and the guide device may be provided. With this configuration, these controls can be performed with only one actuator.

  Appropriate measures can be taken to increase the heating capacity of the air conditioning system during ground operation and during low altitude flight. Various means are available for this purpose.

  The temperature may be increased by recirculating a portion of the compressed air through the compressor. As a result, the temperature of the processing air rises and the heating capacity of the air conditioning system also increases.

  Further, the compressor may be decelerated by increasing the outlet temperature using a valve. Alternatively, the turbine stage may be bypassed.

  Furthermore, the guide device for the turbine can be designed by changing the cross section, which ensures the heating capacity of the air conditioning system under ground conditions.

  Further, the heating capacity can be changed by reducing the amount of ram air. This is done by partially or fully closing the ram air duct by a flap or valve controlled by an actuator. Also, the supply of compressed air to the jet pump in the ram air duct may be reduced or stopped, or the pressure level and throughput may be varied.

  Yet another means is to adjust the power of the impeller installed in the ram air duct.

  The motor can be cooled using outside air or ram air by a liquid refrigerant circuit or a two-phase refrigerant circuit. Another jet pump may optionally be provided in the motor cooling duct. Cooling can be performed using outside air or ram air.

  The water extraction circuit of an air conditioning system typically includes a reheater, a condenser on the compressed air side downstream of the reheater, and a water extractor downstream of the condenser. This water extraction circuit may generally be designed without a reheater.

  According to still another concept of the present invention, there are provided a first air conditioning system and a second air conditioning system that operate according to the method according to any one of claims 1 to 29, wherein the second compressed air supply source is outside air, It is constituted by two compressed air supply sources different from the above, such as two electric compressors or engine bleed air supply sources filled with ram air or pressurized air, and in the second mode both the air conditioning systems One of the two compressed air supply sources is switched on, and the second compressed air supply source of each air conditioning system is switched on in another operating mode. In this method, the compressor switched on or the stream of compressed air supply switched on is first divided into both air conditioning systems, so that the air conditioning is performed when changing from the first operating mode to the second operating mode. It has the advantage that the flow to the first compressor of the system is not reduced so drastically.

  This effect can also be realized by configuring the second compressed air supply source with only one electric compressor or one bleed air supply source filled with outside air, ram air, or pressurized air. In the second mode of operation, the mass reduction of the first compressor is relatively small by switching one second compressed air source at low capacity in both the air conditioning system or the aircraft system. In another mode of operation, the flow mass is relatively large by switching the second compressed air supply in both air conditioning systems.

  A similar dual configuration can also be obtained by connecting the second air conditioning systems or aircraft systems with a connection line. Thereby, when one of the air conditioning units or the system becomes defective, most or all of them can be compensated.

  The details and advantages of the present invention will be described in more detail with reference to the embodiments shown in the drawings.

  FIG. 1 shows a first compressor filled with outside air by reference numeral C1. This is connected to the motor M and the expansion turbine T on one shaft. This whole unit is called MCT (electric compressor turbine). A wavy arrow near the motor M indicates cooling using, for example, a jet pump or a fan. The jet pump or fan is for example arranged in a ram air duct. The same applies to FIGS. 2 and 3.

  Another compressed air supply source, “second air supply source”, is provided in addition to the compressed air supply source, and is switched based on the operation mode of the system. This compressed air supply source can be switched on or off by a valve MV1 (regulating valve 1), and can also be partially switched. A check valve may be provided instead of the valve MV1. The second compressed air supply source may be, for example, a second electric compressor filled with outside air or bleed air from an aircraft engine. The exhaust line of the compressor C1 has a check valve CCKV that ensures that airflow through the exhaust line does not flow in the direction of the compressor.

  The exhaust line of the compressor C1 and the exhaust line of another compressed air supply source are connected to each other at the mixing point 10. The chamber 20 is located downstream of the mixing point and may be provided with a converter for, for example, ozone and / or hydrocarbon (OZC) inside.

  As shown in FIG. 1, the ram air heat exchanger MHX is located downstream of this chamber and is located in the ram air duct 30 of the aircraft. The ram air heat exchanger MHX communicates on the exhaust side with a water extraction circuit comprising a reheater REH, a condenser CON and a water extractor WE. These are arranged in the order of reheater, condenser and water extractor. The exhaust side of the water extractor WE communicates with the low temperature side of the reheater REH. On the exhaust side, the low temperature side of the reheater is connected to and communicates with the upstream side of the turbine T via a guide device VTN (adjustable turbine nozzle). The low temperature exhaust from the turbine passes through the low temperature side of the condenser CON, passes through the check valve PCKV (pack check valve), and is then supplied to the mixing chamber or aircraft cabin.

  As shown in FIG. 1, the water separated by the water extractor WE is supplied to the ram air duct 30 via the water injection device WI. The ram air duct intake valve 32 is installed on the intake side of the ram air duct, and can be moved to various positions by RAIA (ram air intake actuator).

  The ram air duct is divided into two sections 31 and 31 'on the ram air side downstream of the ram air heat exchanger MHX. A jet pump JP is arranged in the upper section and communicates with the exhaust line of the compressor or compressed air supply via a valve JPMV (jet pump regulating valve).

  One line extends from the air-fuel mixture line downstream of the chamber 20 and upstream of the ram air heat exchanger MHX to the exhaust side of the turbine T, and a valve TCV (temperature control valve) is provided therein. It has been. In addition, a bypass line is provided that leads from the exhaust side of the ram air heat exchanger MHX to the line of the air conditioning system that leads to the mixing chamber. A valve BPV (bypass valve) is installed in this line.

  The system of FIG. 1 functions as follows. In the first mode of operation, all fresh air is provided only by the compressor C1. The compressor C1 is preferably a single stage compressor, but may be a multistage compressor. This compressor ensures that the requirements for pressurization, temperature regulation and fresh air supply are met. The exhaust from the compressor passes through the chamber 20 and is first cooled by the ram air heat exchanger MHX. This air then passes through the water extraction circuit and is subjected to a second cooling in a single turbine T of the cooling process. The turbine power becomes the driving force of the compressor C1 together with the power of the motor M. Due to the low temperature exhaust from the turbine, moisture contained in the exhaust from the ram air heat exchanger is condensed in the condenser CON.

  In the second mode of operation, valve MV1 or check valve is opened and a fresh air mass is formed by the exhaust of compressor C1 and the compressed air flow of the second compressed air supply. In the second operating mode, the mixed airflow passes through the same components that the exhaust of the compressor C1 has passed in the first operating mode.

  In the third operation mode, fresh air is supplied first as in the second operation mode. However, due to ambient conditions when the flight altitude is high, opening the valve BPV at least partially bypasses the water extraction circuit and the turbine stage. Cooling in the third mode of operation is performed substantially using the ram air heat exchanger MHX.

  Since each compressor stage by single stage compression requires a high pressure ratio, these compressor stages can only achieve an operating range limited to the corrected mass. In order to be able to output a corrected mass (volumetric flow) as the flight altitude increases, an additional compressor stage or compressed air source is applied to the flight altitude in response to the reduced compressor intake pressure. Switch in parallel according to. The number of outside air compressors used here is not determined, but the entire application area can be covered by connecting in parallel at least two compressed air supply sources per unit (air conditioning system).

  Further, as shown in FIG. 1, the second compressed air supply source may operate the jet pump JP by using an open valve JPMV. This ensures a cooling air flow through the one or more ram air heat exchangers even in the first operation mode. Further, as shown in FIG. 1, the compressed exhaust of the compressor C1 can be supplied to the jet pump via the valve JPMV. This process is particularly practical and ensures safe / stable operation of the compressor C1. The additional mass is directed through the jet pump JP to the ram air duct or supplied to other demand units.

  In order to increase the delivery of the air conditioning system, its cross section can be ideally adjusted by a variable turbine guide device. The unit TVN of the turbine T meets this purpose. This unit can be controlled by a temperature control valve TCV using a normal actuator.

  FIG. 2 shows an example of the configuration of FIG. Here, the second compressed air supply source is composed of a compressor C2 driven by a motor M. Since no turbine is provided, an MC (electric compressor) configuration is obtained. One or more such units may be provided. The operation method of the air conditioning system shown in FIG. 2 corresponds to the method described with reference to FIG. In addition to FIG. 1, recirculation lines that can be closed by a valve ASV (anti-surge valve) extend to the compressors C1 and C2, respectively. In addition, another valve CLV (compressor load valve) is added to the line extending from the chamber 20 to the ram air heat exchanger MHX. When the valve ASV is opened, the recirculated air increases through the compressor. Thereby, the compressors C1 and C2 can be operated safely and stably. As mentioned above, the compressor mass can also be increased by the jet pump regulating valve JPMV. When the valve CLV shown in FIG. 2 restricts the compressors C1 and C2, the outlet temperatures of the compressors C1 and C2 rise.

  FIG. 3 shows still another modification of the air conditioning system that operates based on the method of the present invention. The operation of the air conditioning system described with reference to FIGS. 1 and 2 is an operation at the time of ground operation and at a low altitude flight. According to the configuration of FIG. 3, since the electric compressors C3 and C4 filled with outside air can be switched in stages, the problem that the compressors C1 and C2 of the right or left unit operate in an unstable range is reduced. Is done.

  According to FIG. 3, from a certain flight altitude, only one of the additional compressors C3 and C4 is operated in parallel with the compressors of the left and right units. As a result, the flow masses of the first compressors C1 and C2 do not decrease so much, and the operating point in the stable range (right side of the pump limit (surge line)) is effectively maintained. In order to divide the mass of the compressor (C3 or C4) switched on into both units, the compressors C3 and C4 are connected to each other by a line 40 (cross bleed duct structure). This line is provided with a valve CBSOV (cross bleed shutoff valve) so that the line 40 can be opened and closed.

  By connecting both air conditioning systems with a cross-bleed duct structure, a dual configuration is obtained. Therefore, each air conditioning system can be connected to a compressed air supply source corresponding to the other air conditioning system as necessary.

  When flying at high altitude, another additional compressor (C3 or C4) can also be switched in parallel. The valve CBSOV is closed and the two independent units operate in the same way as in the second mode of operation shown in FIGS.

1 is a schematic view of an aircraft air conditioning system to which the method of the present invention is applied. It is the schematic which shows one Embodiment of the aircraft air conditioning system of FIG. 1 is a schematic diagram of an aircraft air conditioning system for carrying out the method of the present invention.

Claims (31)

An exhaust filled with at least one of outside air, ram air and pressurized air, driven by at least one of at least one motor and at least one turbine and in direct or indirect communication with the aircraft cabin; A method of operating an aircraft system having a first compressed air supply source comprised of a first compressor provided with:
The aircraft system has at least one second compressed air source with an exhaust port that can communicate directly or indirectly with an aircraft cabin;
In the first mode of operation, only the first compressed air source communicates with the aircraft cabin;
In the second mode of operation, both the first and second compressed air sources communicate with the aircraft cabin;
The operation mode is selected according to an outside air pressure, and the first operation mode is set when the outside air pressure is high, and the second operation mode is set when the outside air pressure is relatively low. . The operation method according to claim 1,
Compressed air is cooled by at least one of a ram air heat exchanger and at least one turbine installed in a ram air duct of the aircraft before entering the aircraft cabin. The operation method according to claim 2,
A method of operation, characterized in that at least one turbine is installed on one shaft with the first compressor. The operating method according to any one of claims 1 to 3,
In the second operation mode, the exhaust of the first compressor and at least a part of the exhaust of the second compressed air supply source are mixed, and the mixed airflow is cooled. The operating method according to any one of claims 1 to 4,
A method of operation wherein at least a portion of the exhaust of the first compressor is supplied to a jet pump. The operating method according to any one of claims 1 to 5,
The operation method, wherein the second compressed air supply source is constituted by one or more electric second compressors filled with outside air. The operating method according to any one of claims 1 to 6,
The method of operation, wherein the second compressed air supply source is configured to supply engine bleed air. The method according to any one of claims 1 to 7,
In addition to the first and second compressed air supply sources, another operating method is provided in which another compressed air supply source having an exhaust port capable of directly or indirectly communicating with an aircraft cabin is provided. The method of operation according to any one of claims 1 to 8,
The operation method, wherein the first compressed air supply source and the at least one second compressed air supply source are connected in parallel. The method according to any one of claims 1 to 9,
A water extraction circuit is provided downstream of the compressed air supply source and upstream of the cabin, and a turbine is provided downstream of the water extraction circuit;
Both the first and second compressed air sources communicate with the aircraft cabin and a third mode of operation is set in which compressed air is directed near the water extraction circuit and the turbine by partial or complete bypass. The operation method characterized by being made. The operating method according to any one of claims 1 to 10,
The air is installed on one axis with one or more ram air heat exchangers installed in a ram air duct of the aircraft and the first compressor before entering the aircraft cabin, A method of operation characterized by being cooled by one or more turbines partially filled. 12. The operating method according to claim 1, wherein:
In the first mode of operation, the second compressed air supply is such that the exhaust from the second compressed air supply is supplied to a jet pump installed in a ram air duct with at least one ram air heat exchanger. A method of operation characterized in that a source is connected. The method of operation according to any one of claims 1 to 12,
A method of operation, comprising at least one of a jet pump and a fan for cooling at least one motor driving one or more compressors. 14. A method of operation as claimed in any one of claims 1 to 13,
The second compressed air supply source is constituted by one or more electric second compressors filled with outside air,
At least one of the at least one first and second compressors is provided in the ram air duct with at least one ram air heat exchanger, and at least a portion of the air is routed through the ram air heat exchanger. And operating in a first mode of operation for movement. 15. A method according to any one of claims 1 to 14,
Cooling at least one of one or more of the motors driving the compressor and one or more of the ram air heat exchangers not coupled to the one or more compressors One or more fans are provided. 16. A method of operation as claimed in any one of claims 1 to 15,
The ram air duct has one or more bulkheads extending at least partially in the flow direction to divide the ram air duct into at least two sections;
The first section includes a jet pump communicating with the second compressed air supply source or an impeller coupled to the second compressor,
A method of operation characterized in that air passing through the ram air duct is bypassed by the second section. The operating method according to any one of claims 1 to 16,
A method of operation characterized in that another section is provided in the ram air duct provided with at least one of a jet pump and a fan for cooling the motor. 18. The method of operation according to any one of claims 1 to 17,
Switching from the first operation mode to the second operation mode is performed when the compression limit of the first compressor is reached or when the maximum motor power of the first compressor is reached. Method. The operating method according to any one of claims 1 to 18,
The method of operation characterized in that the air mass supplied to the aircraft cabin during the second mode of operation is larger than the air mass during the first mode of operation. The operating method according to any one of claims 1 to 19,
At least one of the exhaust port of the first compressor, the exhaust port of the compressor of the second compressed air supply source, and the exhaust port of another compressed air supply source is connected to each compressor intake port. An operating method characterized in that a recirculation flow is formed. The operating method according to any one of claims 1 to 20,
At least one of the exhaust of the first compressor and the exhaust of the compressor is supplied to at least one of the second compressed air supply source and another compressed air supply source via a jet pump in the ram air duct of the aircraft. Method of operation characterized in that it is supplied or supplied to a further demand part of said aircraft. The operation method according to claim 21,
The further demand part is selected from the group consisting of OBOGS, OBIGGS, WAI (anti-icing wing), auxiliary cooler / heater, or the exhaust is used to start the engine or auxiliary engine An operation method characterized by that. The method of operation according to any one of claims 1 to 22,
The aircraft air conditioning system has a turbine communicating with an exhaust port of the compressed air supply source,
An operation method comprising: increasing a delivery amount of the aircraft air conditioning system by changing a section of the turbine using a turbine guide device. 24. The method of operation of claim 23, wherein
A line is provided for connecting an intake line of the ram air heat exchanger to an exhaust port of the turbine;
A valve (TCV: temperature control valve) is provided in the same line,
A method of operation characterized in that a common control unit for the valve and the turbine guide device is provided. 25. A method of operation as claimed in any one of claims 1 to 24,
A method of operating characterized in that the temperature is increased by supplying compressed air in a circuit to at least one of the first compressed air supply source and the other compressed air supply source via the compressor. 26. A method according to any one of claims 1 to 25, wherein:
A method of operating, wherein the temperature is increased by restricting at least one of an exhaust line of a compressor of the first compressed air supply source and an exhaust line of the another compressed air supply source. 27. A method of operation as claimed in any one of claims 1 to 26, wherein:
A method of operation characterized in that the temperature is increased by reducing the amount of ram air induced in the ram air duct of the aircraft. 28. The method of operation of claim 27, wherein
Method of operation characterized in that the inlet of the ram air duct can be at least partially closed by using a flap or valve controlled by an actuator. A method of operation as claimed in any one of claims 1 to 28,
The exhaust of the first compressor and the exhaust of the at least one other compressed air supply source are mixed particularly at a mixing point constituted by a chamber that converts at least one of ozone and hydrocarbons. How to operate. 30. A method of operation as claimed in any one of claims 1 to 29.
A first air conditioning system and a second air conditioning system operating by the method according to any one of claims 1 to 29 are provided,
The second compressed air supply source is composed of two or more electric compressors filled with outside air, ram air or pressurized air, or two or more engine bleed air supply sources,
In the second mode, one of the second compressed air supply sources is switched on in both of the air conditioning systems, and in another operation mode, the second compressed air supply source of each air conditioning system is switched on. The operation method characterized by. 31. A method of operation as claimed in any one of claims 1 to 30, wherein
A first air conditioning system and a second air conditioning system operating by the method according to any one of claims 1 to 29 are provided,
The second compressed air supply source is constituted by an electric compressor or an engine bleed air supply source filled with outside air, ram air or pressurized air,
In the second operation mode, the second compressed air supply source is switched on in both of the air conditioning systems to reduce the flow mass,
In another mode of operation, the second compressed air supply source is switched on in both of the air conditioning systems and the flow mass is relatively increased.

Images